A5042171935- Energetic Materials and Combustion
- Rocket and propulsion systems research
- Thermal and Kinetic Analysis
- Combustion and Detonation Processes
- Space Satellite Systems and Control
- Astro and Planetary Science
- Advanced Combustion Engine Technologies
- Spacecraft and Cryogenic Technologies
- Planetary Science and Exploration
- Laser-induced spectroscopy and plasma
- Aerospace Engineering and Control Systems
- Plasma Diagnostics and Applications
- High-Velocity Impact and Material Behavior
- Electrohydrodynamics and Fluid Dynamics
- Heat transfer and supercritical fluids
- Catalytic Processes in Materials Science
- Hydrogen Storage and Materials
- Gas Dynamics and Kinetic Theory
- Electromagnetic Launch and Propulsion Technology
- Fullerene Chemistry and Applications
- Laser-Ablation Synthesis of Nanoparticles
- Synthesis and properties of polymers
- Boron and Carbon Nanomaterials Research
- Combustion and flame dynamics
- Carbon Nanotubes in Composites
Politecnico di Milano
2015-2024
University of Science and Technology of China
2023
Nanjing University of Science and Technology
2017-2023
Space (Italy)
2011-2019
University of Milan
2010-2011
Museo Nazionale della Scienza e della Tecnologia Leonardo da Vinci
1998
George Washington University Virginia Campus
1990
University of Naples Federico II
1988
Princeton University
1973-1976
Recent progress in the synthesis and modification of green oxidizers their application solid rocket propellant formulations during these last few decades are reviewed.
The introduction of nano-sized energetic ingredients first occurred in Russia about 60 years ago and arose great expectations the rocket propulsion community, thanks to higher energy densities faster release rates exhibited with respect conventional ingredients. But, despite intense worldwide research programs, still today mostly laboratory level applications are reported often for scientific purposes only. A number practical reasons prevent at industrial level: inert native coating...
Experiments concerning the ballistic characterization of several nanoaluminum (nAl) powders are reported. Most studies were performed with laboratory composite solid rocket propellants based on ammonium perchlorate as oxidizer and hydroxyl-terminated polybutadiene inert binder. The ultimate objective is to understand flame structure differently metallized formulations improve their specific impulse efficiency by mitigating two-phase losses. Ballistic results confirm, for increasing nAl mass...
In this first paper of a two part study, the ignition response to arc image radiative heating (5 100 cal/cm sec) several double-base propellants is examined; comparisons with certain AP and HMX are made also. Ignition delay affected by chemical factors in propellant formulation (stability condensed phase, reaction rate gas phase) optical (opacifiers affecting reflectivity in-depth absorption). The results show that can only be properly when minimized (as carbon addition). When opacifying...
Oxamide (OXA) and azodicarbonamide (ADA) are among the known burning rate suppressants used in composite solid rocket propellants. Much research has been carried out to understand mechanism of suppression but literature about action OXA ADA on combustion characteristics propellant is still scarce. Here, a systematic study coolant-based propellants undertaken spanning from thermal analyses ingredients variety processes corresponding Thermal gravimetric analysis differential individual...
Experimental studies on the burning of nanoaluminum-based solid rocket propellants are carried out. Data properties condensed combustion products, mechanisms their formation, and burning-rate law obtained. Based these data, a physical picture is developed considered burning-propellant classes. Mathematical modeling nanoaluminum in composite The influence ignition temperature metal fuel shown. results this study allow carrying out analysis selection good-quality using nanoaluminum.
In this second paper of a two-part study, emphasis is on the pressure dependent pre-ignition events in double base propellants and influence radiation source (arc image vs laser) observed ignition behavior. The pressure-dependent (< 21 atm) domain PNC/MTN propellant examined using controlled exposure lengths together with high speed movies an infrared detector to monitor flame development. There brief flux-dependent period transient development after gasification begins; followed by...